Boundary Layer Transition in an Expansion Tube at a Low Enthalpy Operating Condition

McGilvray, Matthew, Jacobs, Peter A., Morgan, Richard G. and Ramanah, Dwishen (2007). Boundary Layer Transition in an Expansion Tube at a Low Enthalpy Operating Condition. In: Proceedings 45th AIAA Aerospace Sciences Meeting and Exhibit. 45th AIAA Aerospace Sciences Meeting and Exhibit, Reno, Nevada, (15826-15837). 8 -11 January, 2007.


Author McGilvray, Matthew
Jacobs, Peter A.
Morgan, Richard G.
Ramanah, Dwishen
Title of paper Boundary Layer Transition in an Expansion Tube at a Low Enthalpy Operating Condition
Conference name 45th AIAA Aerospace Sciences Meeting and Exhibit
Conference location Reno, Nevada
Conference dates 8 -11 January, 2007
Proceedings title Proceedings 45th AIAA Aerospace Sciences Meeting and Exhibit
Journal name Collection of Technical Papers - 45th AIAA Aerospace Sciences Meeting
Place of Publication Reston, VA
Publisher American Institute of Aeronautics and Astronautics, Inc.
Publication Year 2007
Sub-type Fully published paper
ISBN 1563478900
Volume 22
Start page 15826
End page 15837
Total pages 1
Language eng
Abstract/Summary A full flight similarity condition for scramjet testing in an expansion tube was seen ex-perimentally to have a large drop in pitot pressure midway through the test time. This be-haviour has been studied experimentally, numerically and analytically and was determined to be caused by boundary layer transition on the wall of the expansion tube. Compari- son of numerical calculations and experimental measurements of heat transfer on the wall have shown a good agreement of both heat transfer level and transition location, although the numerical simulation does not exhibit the same extent of boundary layer growth after transition. Three possible ways to mitigate the effects of this problem have been suggested while still matching all flow parameters during the test time. These are (1) the use of a gas other than air in the acceleration tube, (2) the use of a reflected shock at the end of the shock tube and (3) the use of the steady nozzle on the end of the acceleration tube. So far, the analysis has shown that use of the steady expansion nozzle will relieve the problems of core flow interruption due to boundary layer transition and allow testing of scramjets in an expansion tube at true flight conditions. This solution also gives the benefit of a longer test time and larger core flow diameter possible with the straight tube configuration. AIAA 2007-1328 Copyright © 2007 by Matthew McGilvray. Published by the American Institute of Aeronautics and Astronautics, Inc., with permission.
Subjects 090107 Hypersonic Propulsion and Hypersonic Aerodynamics
Q-Index Code EX

 
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